Measurements of wall pressure fluctuations and the flow-field were performed to understand the transient behavior of a shock-wave interacting with a Mach 3 boundary layer. Ramps of 10°, 15°, 17.5° and 20° turn angles were used to generate the incident shock-waves. The mean and fluctuating wall pressures were measured underneath the interaction region using flush-mounted high-speed pressure sensors. Schlieren videos with high spatial and temporal resolution were also recorded for each interaction. The mean static pressure profile shows good agreement with theoretical results, and single point statistics of the unsteady pressure signal clearly resolves the impact of the various flow features on the wall pressure. The mean flow features and shock structures are well defined in Schlieren images, and the setup shows strong potential for detailed analysis of unsteady aspects of the flow.
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